Experimental Investigations of Thermomechanical Fluid–Structure Interaction in Rocket Combustion Chambers

Hötte, Felix; Fiedler, Torben; Haupt, Matthias; Lungu, Paul; Sethe, Christoph von; Haidn, Oskar

doi:10.2514/1.b37439

Cited by 12 publications

(5 citation statements)

References 8 publications

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“…This test segment is made of the copper alloy CuCr1Zr and has a realistic cooling channel geometry for nitrogen as coolant. For details on the test bench and the experimental conditions, see [3].…”

Section: Subscale Combustion Chambermentioning

confidence: 99%

“…Since the subscale test chamber was originally designed to provoke a damage of the cooling channel [3], the thin combustion chamber wall buckled in some areas. This caused a partial delamination of the coatings, see Fig.…”

Section: Subscale Combustion Chambermentioning

confidence: 99%

“…Copper liners of liquid fuel rocket engines are subjected to high thermomechanical loads which can lead to damage by blanching [1][2][3] or the so-called doghouse effect [4][5][6][7][8][9]. To avoid failure, a thermal barrier coating (TBC) may be applied on the inner surface of the combustion chamber.…”

Section: Introductionmentioning

confidence: 99%

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Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics

Fiedler

Rösler

Bäker

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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To protect the copper liners of liquid-fuel rocket combustion chambers, a thermal barrier coating can be applied. Previously, a new metallic coating system was developed, consisting of a NiCuCrAl bond-coat and a Rene 80 top-coat, applied with high velocity oxyfuel spray (HVOF). The coatings are tested in laser cycling experiments to develop a detailed failure model, and critical loads for coating failure were defined. In this work, a coating system is designed for a generic engine to demonstrate the benefits of TBCs in rocket engines, and the mechanical loads and possible coating failure are analysed. Finally, the coatings are tested in a hypersonic wind tunnel with surface temperatures of 1350 K and above, where no coating failure was observed. Furthermore, cyclic experiments with a subscale combustion chamber were carried out. With a diffusion heat treatment, no large-scale coating delamination was observed, but the coating cracked vertically due to large cooling-induced stresses. These cracks are inevitable in rocket engines due to the very large thermal-strain differences between hot coating and cooled substrate. It is supposed that the cracks can be tolerated in rocket-engine application.

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Section: Subscale Combustion Chambermentioning

confidence: 99%

Section: Subscale Combustion Chambermentioning

confidence: 99%

See 1 more Smart Citation

Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics

Fiedler

Rösler

Bäker

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

Self Cite

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“…The turbine blades located within aircraft engines and high-speed rotating blades play a crucial role in drawing in high-temperature and high-pressure air into the burner to maintain engine operation [3]. The rocket engine combustion chamber is a device that facilitates the burning of fuel or propellant to produce high-temperature gas, and it is exposed to a high-temperature environment for an extended period [4]. The flight process of hypersonic vehicles involves extremely high speeds, resulting in strong shock compression and viscous blocking of the gas surrounding the vehicle, leading to the formation of a high-temperature and high-pressure aerodynamic thermal environment [5].…”

Section: Introductionmentioning

confidence: 99%

Review on Creep Phenomenon and Its Model in Aircraft Engines

Yuan,

Chenglong,

Yongchao

et al. 2023

International Journal of Aerospace Engineering

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The aircraft is subjected to high-temperature and high-pressure conditions during flight, which renders it susceptible to the occurrence of creep phenomenon. Several academics have conducted extensive research on this issue. This research paper provides a comprehensive overview of the existing literature on creep phenomena in aircraft engines. First, several classical creep calculation models are enumerated and categorized as creep life calculation, creep-fatigue life calculation, and creep deformation calculation. Studies on creep phenomena are conducted in various components of aircraft engines, such as the engine’s turbine blades, turbine disks, and combustion chambers. The creep behavior of turbine blades in aircraft engines has been extensively researched. Furthermore, the protective measures aimed at mitigating creep are presented. Materials with high creep resistance can be used, and alternative fuels could be implemented. This paper provides an in-depth analysis of the advantages of creep in aircraft, presented in a favorable perspective. Finally, the prospective future research direction is discussed.

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“…In other words, rockets can also function as equipment to maintain sovereignty. The design of rocketry technology, both in terms of the rocket and its payload, starts from the design stage, manufacturing, testing to flight testing [2].…”

Section: Introductionmentioning

confidence: 99%